Supercharging system for aircraft



Dec. 8, 1936'. F. YOUNG ET AL SUPERCHARGING SYSTEM FOR AIRCRAFT Filed July 16, 1934.

Patented Dec. 8, 1936 aosam sornnonsnomo SYSTEM FOR Antonin Franklin Young, Glendale, and Richard I.

Hardin, Los Angeles, Calif.

Application July 16, 1934, Serial'No. 735.449

2 Claims.

This invention, in its broadest aspect, comprehends the provision of means for connecting a power generating mechanism, such as an internal combustion motor, with a supercharging mechanism, whereby air of a density greater than that of the normal density at the location of the motor may be injected into the fuel feeding apparatus of the motor, in order that the motor may be operated at high altitudes with the same eficiency and under conditions approximately typical of lower altitudes.

In the application of our improved system of supercharging we may vary the connections and arrangement of the several elements for the system to'meet diflerent operating conditions and local requirements. For instance: when applied to a stationary motor'the fuel intake may be connected with a source of compressed air of a density substantially corresponding to the density of the atmosphere at sea level or at agiven elevation above sea level. mounted adjacent to or cle in which the air is held under compression with the exhaust open to the atmosphere and the fuel intake open'to the air in the receptacle.

Our system is particularly adapted for use in connection with aircraft in whi ch is provided either a receptacle for holding air under comcompression or a cabin sealed against the en-' trance of air from the atmosphere except as may he required, in the opinion of the pilot and in such case under his control. m system also contemplates the provision of means included in the The motor may he connections with motor for heating the air from the atmosphere as it is induced into the cabin for maintaining a substantially uniform temperature therein at difterent altitudes, means for cooling the air at will, suitable devices for relieving excess pressure in the cabin and connections, a supercharging pump operated by the motor and valves tor selectively connecting the fuel intake with the cabin or the atmosphere, or

shcth, and for otherwise rendering the system flexible and sclently comprehensive to meet varying atmospheric conditions.

our system is particularly adapted for use on aircraft it will be obvious that the same may be used with equal success on other types of stationary and automotive power plants.

A particular object, therefore, is to provide a supercharging system for aircraft with a power mechanism and a sealed cabin, means connecting the cabin with the power mechanism where* Toy air at less than a 'given density may be compressed in the cabin to a density in excess of the density of the atmosphere at a given altitude and exhausted from the cabin to and for'use in the operation of power mechanism.

Other objects may appear as of our system proeresses.

the description within a sealed recepta he installed in the air convenient to the pilot.

We have shown a practical application of our invention'to an aircraft motor and cabin in the accompanying drawing in which:

Fig. l is a sectional plan of an airplane motor and cabin showing connections suitable for the operation of our superchar System;

Fig. 2 is a sectional elevation of an air heater connected with the motor of heating the air from the atmosphere before it is conducted to the cabin; 'as seen on line 2--2 of Fig. 1;

Fig. 3 is a typical section of one of several valves employed in the connections between the motor, the cabin and the super-chargin pinup,

for varying the temperature and changing the route of the air in its travel to the motor.

In said drawing A represents thehcod of an airplane within which is housed a motor M disposed forwardly of cabin C which in this instance is constructed so as to be air tight and thus not in communication with the external atmosphere. A suitable superch g pump 8' is operatively connected with the motor 312 so that air from the atmosphere may be induced into the sealed cabin C at will, or directed to the fuel intake 2 of the motor.

A heater H may be provided adjacent the mo tor M so that air passing therethrough the supercharger S may or the motor, and a cooler B may also be connected in the-air lines intermediate the motor and the cabin for cooling the air when required. Suitable thermostats and pressure gauges may lines for maintaining anhstantiaily uniform temperature and pressure in the cabin. Such devices have not been shown in. the drawingand will not he described herein as their application to the system inasmuch as their use is well known.

Intermediate the cabin Candi hood. A is the operating devices may be mounted-in positions sealed against the atmosphere the the hood is not necessarily airtight and is usually open to the atmosphere.

Two air intakes from the amosphere are provided at 2 and 3 for selective connection with the supercharger S, .as shownin Fig. l. The foremost intake heater H, as shown in Fig. 2,- and leads. to a three way valve 4 to which the rearmost intake 3 also is connected (see Fig. 3). Heater H has a heat inlet 5 open to the chamber 8 of the heater and connected with the exhaust manifold l of the motor, and an outlet I leads from chamber 6 outwardly of the hood A to the external atmosphere. Thus air from the atmosphere is conducted through the heater by means of pipe 2 to'valve .4 and thence from said valve through a pipe I to the inlet ll of the supercharger S.

be heated fiom the exhaust While the cabin is, space within Valve 4 has an operating rod H extending through panel I and provided within the cabin C with a handle l2, whereby the air may be delivered to the supercharger selectively from either-0f pipes 2 or 2, as desired.

The valve 4 may be of the form shown in Fig. 3, or otherwise, but in any event so arranged that the valve 'V may be turned through the instrumentality of the handle l2 for establishing communication between pipes 2 and 8 (as shown) for delivering heated air to the supercharger, or reversely turned to an extent of 90 degrees for establishing communication between pipes 3 and 9, whereby air from the atmosphere may be delivered to the supercharger.

The outlet of the supercharger is connected with a three way valve l3 which is similar to valve 4 as by means of a pipe l4 and is provided with an operating stem l5 and a handle it on panel board i. Air from the supercharger is discharged into the cabin C through a pipe IT, a shut off valve l8 and an inlet section I!) which is open to the cabin, as shown in Fig. 1. Valve I8 is operated by means of a suitable stem 20 and a handle 2i.

Air from the cabin is discharged under pressure into an outlet pipe 22 leading to a three way valve 23, similar to valves 4 and It and adapted to be operated from the cabin by means of a stem 24 and a handle 25. A pipe 26 connects valve 23 with pipe l1, and intermediate valves l3 and 23 we provide an air cooler B of suitable design which is connected with valve l3 and pipe 26, as shown. Said cooler may be employed for cooling the air from the supercharger by adjusting valve I 3 so as to by-pass the air through pipes 25 and i7, valve '8 and pipe IS to the cabin, all of which is possible only when the valve 23 is properly operated for such purpose.

The fuel intake F of the carburetter attached to motor M connects with valve 23 by means of a pipe 28 and a branch pipe 29 in which is arranged a check valve 39, and pipe 29 is provided with a combined pressure operated and manually operable relief valve 35 to which is attached an exhaust pipe 32 leading to the atmosphere. Valve 3i may be operated by the pilot by means of a rod 33, or as in commercial types of such valves the same will be automatically operated by excess pressure in the line Mtween intake F and valve 23, as in the case of a back flre of the motor.

An auxiliary relief valve 34, similar to valve Si, is provided on the cabin wall for relieving excess pressure in the cabin and is also operable by the pilot by means of an operating member 35 when it may be desired to lower the pressure in the cabin.

In operation, air is delivered from the atmosphere, either through intake 2 or 3 to the supercharger and thence to the cabin through inlet 20 either by or without passing the air through the cooler B, by properly adjusting the valves 12 and 23, as maybe desired or required. Air to meet the requirements of the motor is discharged from the sealed cabin C through outlet 22 while valve 23 is closed to pipe 26 and thence through pipes 29 and 28 to the carburetter intake 1''.

The air from the atmosphere may be admitted partially through pipes opening of valve 4, thereby cooling the air to a desired extent without the use of the cooler B.

2 and 3 by the partial In all exists the system shown and described is flexible and comprehensive so as to operate the airplane under different and variable conditions and to insure delivery of proper volume of air of a suitable density to the motor from the supercharger or from the cabin and a suflicient volume of fresh air to the cabin.

From the foregoing description 04 our system it will be obvious that we have devised a method and means for supplying air of greater density than the air of the atmosphere at altitudes above sea level. It is well known that airplane and other types of motors operate at substantially less than sea level emciency when in high altitudes, due to the lack of oxygen whereas by the use of our method and means for compressing the air for delivery to the motor, sufiicient additional volumes of oxygen are stored in the cabin for delivery to the motor to compensate for the rarity of the element in the external atmosphere.

High speeds of aircraft are more possible in high altitudes than at lower levels, but as the altitude of flight increases the efilciency of the motor, is correspondingly decreased and the discomfort to passengers is increased, due to the gradually lowering atmospheric pressure. When, however, the pressure is maintained at a substantially uniform point regardless of altitude, as by means of our system, the comforts of flight and engine efiiciency are likewise maintained to a correspondingly uniform extent. Thus greater eiliclency increased the speed of flight, and increased passenger travel is induced by higher speed and greater comforts of travel.

What we claim is:

1. A supercharging system for aircraft comprising: a substantially air-tight cabin, a motor having a fuel inlet, a supercharger operatively connected with said motor and including an inlet and an outlet, an air inlet to and an air outlet from said cabin, means for delivering air from the atmosphere to the inlet of said supercharger, means for independently or simultaneously delivering air from said supercharger to said cabin and said fuel inlet, and plural control means in the connections between said cabin, said supercharger and said fuel inlet, for selectively regulating the flow of air directly from said supercharger and from said cabin to said fuel inlet.

2. A supercharging system for aircraft comprising: a substantially air-tight cabin, a motor having a fuel inlet, a supercharger operatively connected with said motor and including an inlet and an outlet, an air inlet to and an air outlet from said cabin, means for delivering air from the atmosphere to the inlet of said supercharger, means for independently or simultaneously delivering air from said supercharger to said cabin and said fuel inlet, said last mentioned means including a valve interposed between the outlet of said supercharger and the inlet to said cabin, a by-pass between said valve and the inlet to said cabin, a second valve between said by-pass and said outlet to said cabin, a connection between said by-pass and said fuel inlet, and means for controlling the inlet to said cabin for controlling the exhaust of air to the atmosphere, whereby air from said supercharger or from said cabin may be selectively supplied to said fuel inlet.

Eli 

